Internal-combustion turbine-engine



G. H. HEMINGWAY.

INTERNAL COMBUSTION TURBINE ENGINE. I

arucmou FILED APR. I8, 1919. S

Patented Feb. 24,1920. j

2 SHEETS-SHEET I.

G. H. HEMINGWAY. INTERNAL COMBUSTLON TURBINE ENGINE. APPLICATION FILED APR. 18. [91 9- 1,331,766. I Patented Feb. 24,1920.

2 SHEETS-SHEET 2.

'rmmzmn rrn I llllllllll LlLl W STATES-PATENTf Omen GEOfiG-E HENRY SEEING-WAY, OF'COVENTBY, ENGLAND.

combination with a turbine of an nr'crnnirmcounusrroiv TURBINE-ENGINE.

entry, in the county of Warwick, England,

' have invented certain new and useful Imto Internal-Comprovements in or Relating 15 which the folbustion Turbine-Engines,

- lowing is a specification.

This invention relates to internal combustion turbine engines, and consists of the rotary compressor.

The improvements have for their main object the initial induction of the gases through the rotary compressor, which rotary compressor may or may with a super-compressor w 'ch may arranged intermediately between the initial rotary compressor and the turbine.

The object of he super-compressor is to obtain increased compression of the gaseous mixture after initial compression the rotary compressor and prior to ignition, the improvements also embodying in combination with the rotary type of initial compressor, means for shutting off the charge, which charge is then subjected to the additional or super-compression prior to its ignition and explosive operation on the turbine, the whole arrangement, including the rotary compressor,= super-compressor and turbine preferably comprising a single unit.

in order that this invention may be clearly understood and readily carried into practice,

reference may be had to'the appended explanatory two sheets of drawings, upon which:-

Figure 1 is a part sectional and part elevational plan of one embodiment of the invention. I 2 is a part sectional and part elevational plan illustrating another embodiment of the invention.

i In an embodiment of this invention the a rotary compressor a for effecting initial compression is arranged adjacent to the oneend of the main shaft 6, the turbine 0 being arranged at or adjacent to the other end of the main shaft 5. Two oppositely positioned ducts or assages d are provided for the passage of t e mixture from the rotary to the turbine '12. The rotary compressor a at each duct is provided at its inner end with a revolving disk .a having Specification of Letters man.

initial 7 not be combinedof a connecting rod through Patented Feb. 24', 1920.

Application ma April 18,1519. Serial Io. 291,018.

ports a? which permit the gaseous mixture shaft b in opposite directions and in relation to the respective passages.

Behind each revolving disk above mentioned on the inside ofthe compressor or the side adjacent to the super-compressor, a sprin rin d is arranged to make contact with the disk at and prevent any back pressure or escape of Each super-com ton e which is a of the passage, formed to receive the slide valve 6, the said piston being operated through the medium 0 by an. eccentric e on the main shaft. A slide valve e in the form of a sleeve around the piston is also, operated through the medium of a rod or rods 6 by eccentrics e on the main shaft '6.

The sleeve 6 forming the slide valve is provided with orts e e, the one 6'' of which is adapted passage through which the mixture passes from the rotary compressor a. Thiscuts gas.

apted to'enter a part d theducts between the com I ressor e comprises a piswhich part is cylindrically to shut off that part of the v oil the gases from the rotary compressor a,

in addition to the disk a having ports from the rotary compressor. The action of the sliding valve 6 and piston e is so timed that the slide valve 6 first closes the port 6 to the passage adjacent to the rotary compressor a, after which the advance of the piston e in the cylindrical part d ofthe sliding valve 6 efr'ects a super-compression of the gases in that part of the passage d between the super-com ressor and the turbine c.

The ignition plug is arranged at fiin that part of the passage d adjacent to the entrance of the turbine c, the passage at this point being chamber. The entrance between the chamber and the turbine is provided with a fixed grille'or nozzle plate 65 comprised of a series of inclined blades which direct the gases formed by the explosion against the blades 0 which are radially arranged in ports in ally arranged blades being preferably laterally inclined. In addition, spring rings enlarged to form an explosion,

d on that side of the piston d are fitted at the entrance to the turbine to prevent any escape of the compressed gases previous to ignition.

The turbine 0 preferably consists of a series of radially arranged blades a, a. The first set of blades fixed into the turbine drum are so arranged as to be exposed to the explosive gases durin being in a reverse position to those which are rotated, while the ends of the blades are secured respectively to the rotating drum 0* and inner circumference of the casing by a series of pairs of rings 0 between each alternate pair of which a dovetailed annularchannel is formed, in which the ends of the blades which are of a dovetailed shape are fitted, suitable dovetail s acing plugs bein provided between the end of the blades, an

each pair of rings riveted together to prevent disassembling the whole'bein secured and retained in position by adjusta le screw pins in fixed rings 0 the ends of which screw pins impinge against the outer of the pairs of rings 0, thus enabling the whole of the rings to be forced tightly together. The rings 0 are prevented from sliding back by shouldering against split spring rings which spring into grooves formed into the rotating drum and casing respectively.

The rotary compressor a may be of any suitable type, such for instance as that type which embodies a series of rotating impellers which are directl secured to the main shaft and surrounded by a series of passages for collecting and diverting the gases from one stage of compression to the next. These latter air passages are secured to the internal circumference of the casing of the compressor and may be water cooled by jacket it.

Two or more entrances 9 arranged on the opposite sides of the main shaft are provided for the entrance of gas or mixture to the rotary compressor.

The rotary compressor a, super-compressor e and turbine 0 with intervening passage d are all water cooled by jackets as also the interior of the drum 0 carrying the rotating blades of the turbine, such water cooling of the drum being effected through the interior of that end of the main shaft which may be bored for the purpose. Also the fixed grille or nozzle plate d may be Water cooled by means of Water connections to j aczets k.

the time of the firing only, the other portion of this first or outer Other turbine blades a are In another embodiment of this invention,

as illustrated by Fig. 2, the turbine 0 may.

pression are adapted to have a reciprocating,

movement which is parallel to the main shaft, such movement being obtained through the madium of projecting rollers m and m which are attached to the respective pistons e and slide valves 6 and which are operated by rotating worm cams m and m which are mounted on the end of the main shaft 6.

The operation of the piston e and slide valve e for obtaining the super compression in place of being effected by eccentrics or cams as previously described may be effected by ordinary lift cams, or by cranks.

It will be readily understood that by the shutting ofi of the mixture by the rotating disk a in the rotary compressor a and the sleeve valve 6 in the super-compressor, that any. possibility of back firing is obviated, and also that by shutting off of the turbine blades before the period of firing any loss of compression is also obviated.

What I claim as my invention and desire to secure by Letters Patent is 1. An internal combustion engine comprising a turbine, a compressor located 00-.

axially therewith, and means to increase the compression between said turbine and said compressor, said pressure increasing means also. serving to deliver the charge prior to ignition and to seal the ingress of the charge to the explosion space of the turbine.

2. An internal combustion engine comprising a turbine, a compressor located. coax'ially therewith, and means to increase the compression between said turbine and said compressor, the said compressor being arranged for rotation and being provided with means rotating therewith for shutting 0% the charge after compression and prior to ignition.

3. A turbine internal combustion engine and rotary compressor having intermediate to the compressor and turbine a super compressor including a piston and a sleeve valve concentric with said piston.

4:. In an internal combustion engine, a turbine having afixed drum and a rotating drum; and also'having blades fixed to said drums, rings on said drums, and adjustable screws engaging said rings and causing the same to retain the blades in place.

In witness whereof I have hereunto set my hand in the presence of two witnesses.

GEORGE HENRY HEMINGWAY. Witnesses:

ARTHUR H. Brown, EDGAR N. Wrmmm. 

